XFOIL Version 6.96 Calculated polar for: NACA M7 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.000 -0.4600 0.08550 0.08310 0.0345 0.7221 0.0084 -6.750 -0.4624 0.08175 0.07931 0.0326 0.7158 0.0086 -6.500 -0.4627 0.07798 0.07553 0.0312 0.7086 0.0089 -6.250 -0.4561 0.07405 0.07153 0.0285 0.7025 0.0093 -6.000 -0.4461 0.07007 0.06750 0.0252 0.6957 0.0095 -5.750 -0.4333 0.06602 0.06335 0.0224 0.6896 0.0095 -5.500 -0.4190 0.06190 0.05915 0.0205 0.6830 0.0096 -5.250 -0.4043 0.05772 0.05488 0.0192 0.6766 0.0096 -5.000 -0.3887 0.05358 0.05065 0.0182 0.6704 0.0096 -4.250 -0.3796 0.05695 0.05350 0.0215 0.6661 0.0098 -4.000 -0.3632 0.05337 0.04980 0.0212 0.6597 0.0100 -3.750 -0.3430 0.05032 0.04668 0.0208 0.6524 0.0102 -3.500 -0.3204 0.04745 0.04367 0.0204 0.6459 0.0105 -3.250 -0.2962 0.04464 0.04074 0.0201 0.6390 0.0108 -3.000 -0.2710 0.04192 0.03786 0.0200 0.6327 0.0112 -2.750 -0.2449 0.03924 0.03503 0.0200 0.6263 0.0117 -2.500 -0.2179 0.03662 0.03222 0.0202 0.6198 0.0124 -2.250 -0.1889 0.03412 0.02950 0.0207 0.6140 0.0132 -2.000 -0.1567 0.03208 0.02725 0.0215 0.6076 0.0140 -1.500 -0.1044 0.02554 0.02017 0.0232 0.5962 0.0148 -1.250 -0.0795 0.02388 0.01836 0.0233 0.5900 0.0158 -1.000 -0.0521 0.02212 0.01640 0.0238 0.5841 0.0175 1.000 0.1765 0.01140 0.00393 0.0280 0.5369 0.0220 1.250 0.2039 0.01095 0.00340 0.0284 0.5314 0.0212 1.500 0.2303 0.01030 0.00272 0.0289 0.5242 0.0229 1.750 0.2575 0.01002 0.00236 0.0292 0.5146 0.0250 2.000 0.2854 0.00984 0.00212 0.0293 0.5042 0.0260 2.250 0.3134 0.00973 0.00196 0.0294 0.4967 0.0297 2.500 0.3407 0.00950 0.00196 0.0295 0.4893 0.1417 2.750 0.3682 0.00932 0.00197 0.0295 0.4810 0.2166 3.000 0.4357 0.00793 0.00249 0.0209 0.4690 0.9907 3.250 0.5022 0.00823 0.00270 0.0123 0.4540 1.0000 3.500 0.5294 0.00826 0.00267 0.0123 0.4409 1.0000 3.750 0.5566 0.00831 0.00265 0.0123 0.4237 1.0000 4.000 0.5840 0.00841 0.00266 0.0122 0.4036 1.0000 4.250 0.6115 0.00854 0.00269 0.0120 0.3783 1.0000 4.500 0.6391 0.00875 0.00279 0.0118 0.3448 1.0000 4.750 0.6670 0.00913 0.00294 0.0113 0.2945 1.0000 5.000 0.6974 0.01048 0.00359 0.0093 0.1491 1.0000 5.250 0.7260 0.01168 0.00431 0.0079 0.0504 1.0000 5.500 0.7521 0.01197 0.00462 0.0080 0.0471 1.0000 5.750 0.7781 0.01231 0.00501 0.0080 0.0445 1.0000 6.000 0.8040 0.01272 0.00547 0.0081 0.0423 1.0000 6.250 0.8298 0.01320 0.00603 0.0080 0.0410 1.0000 6.500 0.8553 0.01376 0.00668 0.0080 0.0403 1.0000 6.750 0.8803 0.01439 0.00742 0.0080 0.0400 1.0000 7.000 0.9049 0.01508 0.00820 0.0080 0.0399 1.0000 7.250 0.9287 0.01589 0.00910 0.0080 0.0397 1.0000 7.500 0.9518 0.01669 0.00996 0.0082 0.0395 1.0000 7.750 0.9742 0.01754 0.01091 0.0084 0.0394 1.0000 8.000 0.9957 0.01846 0.01190 0.0089 0.0394 1.0000 8.250 1.0166 0.01940 0.01290 0.0094 0.0394 1.0000 8.500 1.0369 0.02036 0.01393 0.0101 0.0394 1.0000 8.750 1.0576 0.02114 0.01479 0.0108 0.0391 1.0000 9.000 1.0800 0.02137 0.01513 0.0113 0.0377 1.0000 9.250 1.1005 0.02195 0.01580 0.0118 0.0359 1.0000 9.500 1.1199 0.02270 0.01662 0.0125 0.0341 1.0000 9.750 1.1383 0.02347 0.01744 0.0131 0.0319 1.0000 10.000 1.1536 0.02481 0.01882 0.0140 0.0299 1.0000 10.250 1.1660 0.02701 0.02118 0.0154 0.0276 1.0000 10.500 1.1860 0.02665 0.02095 0.0156 0.0258 1.0000 10.750 1.2052 0.02663 0.02103 0.0157 0.0230 1.0000 11.000 1.2245 0.02666 0.02107 0.0155 0.0205 1.0000 11.250 1.2441 0.02698 0.02147 0.0154 0.0173 1.0000 11.750 1.2893 0.02736 0.02186 0.0145 0.0115 1.0000 12.000 1.2961 0.02888 0.02340 0.0150 0.0102 1.0000 12.250 1.2921 0.03171 0.02631 0.0153 0.0092 1.0000 12.500 1.2911 0.03449 0.02924 0.0153 0.0087 1.0000 12.750 1.2925 0.03711 0.03202 0.0152 0.0082 1.0000 13.000 1.2920 0.04000 0.03505 0.0149 0.0078 1.0000 13.250 1.2908 0.04300 0.03819 0.0146 0.0075 1.0000 13.500 1.2887 0.04617 0.04150 0.0142 0.0072 1.0000 13.750 1.2854 0.04951 0.04498 0.0136 0.0070 1.0000 14.000 1.2809 0.05309 0.04869 0.0128 0.0068 1.0000 14.250 1.2744 0.05696 0.05269 0.0119 0.0066 1.0000 14.500 1.2662 0.06115 0.05703 0.0109 0.0064 1.0000 14.750 1.2557 0.06576 0.06179 0.0096 0.0063 1.0000 15.000 1.2440 0.07082 0.06701 0.0080 0.0062 1.0000 15.250 1.2314 0.07623 0.07259 0.0061 0.0061 1.0000 15.500 1.2173 0.08216 0.07869 0.0038 0.0060 1.0000 15.750 1.2019 0.08852 0.08523 0.0012 0.0060 1.0000 16.000 1.1867 0.09514 0.09201 -0.0018 0.0060 1.0000 16.250 1.1713 0.10205 0.09908 -0.0050 0.0060 1.0000 16.500 1.1555 0.10929 0.10647 -0.0085 0.0060 1.0000 16.750 1.1398 0.11682 0.11414 -0.0122 0.0060 1.0000 17.000 1.1239 0.12464 0.12209 -0.0161 0.0060 1.0000 17.250 1.1082 0.13276 0.13034 -0.0203 0.0061 1.0000 17.500 1.0916 0.14148 0.13919 -0.0248 0.0062 1.0000